Detent rib



Sept. 23, 1969 ALPERT 3,468,215

DETENT RIB Filed May 31, 1968 INVENTOR.

L O U 15 AL P ERT ROY MILLER A TTOR/VEY 3,468,215 DETENT RIB Louis Alpert, China Lake, Calif., assignor to the United States of America as represented by the Secretary of the Navy Filed May 31, 1968, Ser. No. 733,455 Int. Cl. F41f 3/04 US. Cl. 891.8 1 Claim ABSTRACT OF THE DISCLOSURE A removable steel rail which is adapted to be fastened to the forward motor skirt and to the rear ejection boss of a missile motor. The rail has a machined recess to accept the launcher forward detent and another recess near the aft end which accepts the ejection kicker.

Background of the invention The purpose of the present invention is to provide an adapter for a missile to preclude spring actuated return of the launcher forward detent to its prelaunch position until the missile is lear of the launcher. The adapter or detent rib must meet the structural and interface requirements imposed on the system in order to assure system compatibility and must be capable of being field-retrofitted to existing rocket motors with a minimum of special skills and equipment.

Summary of the invention The invention comprises a detent rib which is afiixed to a missile motor case to make the missile motor case interface to the launcher the same as the motor case interface for which the launcher was originally designed.

Description of the drawing FIGS. 1 and 2 illustrate the problem which is overcome by the present invention wherein FIG. 1 shows a missile in captive flight and FIG. 2 depicts the missile during launch;

FIG. 3 illustrates a preferred embodiment of the invention; and

FIG. 4 is a side elevation of the launcher.

Description of the preferred embodiment In describing the preferred embodiment of the invention reference is made to FIGS. 1 and 2 to illustrate the problem which is overcome by the invention. FIG. 1 illustrates a missile in position in captive flight on a launcher 11. The missile 10 illustrated in FIGS. 1 and 2 has a smaller diameter motor case than the one for which the launcher was designed. A forward detent rib 12 engages a forward detent 13 on the launcher 11. An aft launch hook band 14 with an integral aft detent boss and jettison surface is attached to the after end of the motor case of the missile 10. At time of launch the motor is ignited and the forward detent 13 is pushed forwardly once the motor pressure exerts a force of approximately 1,000 pounds on the forward detent. As the missile 10 moves forward the launcher forward detent 13 returns to its original position after disengaging the forward detent 12 on the motor case. Interference then occurs between the launcher forward detent 13 and the aft detent boss. Interference between the launcher forward detent and the motor aft detent boss results in sheared pins in the launcher which requires dis- 3,468,215 Patented Sept. 23, 1969 assembly and rework of the launcher subsequent to each launch.

FIG. 3 illustrates the preferred embodiment of the invention wherein a detent rib 30 is illustrated attached to a motor case 31. The detent rib 30 extends between a forward launch hook 32 and just aft of an aft launch hook 33. The detent rib 30 is secured to the motor case at its forward end by means of pins 34 which are inserted through holes 35 in the forward portion of the detent rib. There is a machined recess in the rearward portion of the detent rib 30 and a jettison surface 38 on the recess. The detent rib after end is secured to the aft launch hook 33 by means of two screws 39 and 40.

The detent rib 30 has a top surface which is free of any indentations or projections excluding the forward detent recess 36 and aft detent recess 37. Thus, the detent rib detent to its prelaunch position once the motor is fired mechanically prevents the return of the launcher forward until the motor aft detent clears the forward detent.

In operation (with further reference to FIG. 4) the rib detent 30 supports arrested landing loads input through the forward detent 13 as a tension member suspended from the forward skirt and as a column to the aft launch hook 33. The catapult launch loads when an aircraft is launched are supported through compression into the aft launch hook 33 also.

The loads input due to a launcher malfunction at launch, i.e., ignition and launch with the launcher in the locked position, results in a high forward detent load in conjunction with full motor pressure. This results in an addition of the tensile loads in the forward rib 32 forward of the forward detent 13 with a partial canceling of the tension loads aft of the forward detent.

As shown in FIG. 4 the forward detent 13 on the launcher 11 has two functions; the first being to retain the motor on the launcher 11 when it is subjected to accelerations such as on arrested landings, and the second is to provide restraint for the motor until a certain thrust level is developed. Aft detent 41 on the launcher simply retains the motor on the launcher 11 when it is subjected to accelerations during catapult take-off or aerodynamic drag forces. The aft detent 41 is interconnected with a jettison mechanism 42 and is permitted to rotate out of position during the jettison sequence which moves the motor off the launcher backwards. The jettison kicker 42 is a mechanism in the launcher, which as described above, unlocks the aft detent and rotates around, thereby pushing the motor off the launcher by applying a force through the jettison surface 38 (of FIG. 3). Forward and aft rails 43 and 44 respectively, on the launcher provide the launcher motor connection and guide the motor during its first eight inches of movement during launch.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is, therefore, to be understood that within the scope of the appended claim the invention may be practiced otherwise than as specifically described.

The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

What is claimed is:

1. Apparatus for adapting a first type of missile for launch from a missile launching system designed for launching a second type of missile of a different size comprising:

3 4 a launcher for supporting and guiding a missile of the from returning to a prelaunch position until the rear second type; detent recess has passed by the forward detent. forward and rear detent means on said launcher; References Cited a detent rib adapted to be fixedly attached to said first type f missile; 5 UNITED STATES PATENTS said detent rib having a forward recess adapted to re- 2,659,274 11/ 1953 Lauritsen 89-1.819 *ceive and coact with said forward detent means; 2,809, 9 10/1957 Lauritsen 891.819 said detent rib having a recess at the rearward end 3,215,040 11/ 1965 KOSS n et a1. 891.819

adapted to recelve and coact with the rear detent; 1O SAMUEL W ENGLE Primary Examiner sald rearward recess having a ettison surface adapted to cooperate with a jettison kicker on said launcher; C1- said detent rib functioning to prevent the forward detent 

